摘要
可重复使用液体火箭发动机对冲击式涡轮叶片疲劳寿命的验证需求越来越强烈,然而,目前叶片疲劳试验以成本高昂的搭载试车为主,且冲击式涡轮叶片尺寸小,试验难度大。为此,本文以某型液体火箭发动机涡轮一级动叶为研究对象,建立了小尺寸液体火箭发动机涡轮叶片疲劳寿命仿真与试验室考核方法,从理论和试验的角度对叶片疲劳寿命实验室考核试验的可行性和合理性进行了论证。本文的研究可以为液体火箭发动机涡轮叶片和其他部件疲劳寿命的评估提供参考。
There is a growing demand for the fatigue life verification of impulse turbine blades in reusable liquid rocket engines.However,at present,the blade fatigue experiment is mainly carried out with the high cost rocket engine test,and the size of impulse turbine blades is small,so the individual test is difficult.Therefore,the first stage rotor blade of a certain type of oxygen turbine is taken as the research object in the current work.The laboratory assessment method for the fatigue life of small-size liquid rocket engine turbine blade is established,and the feasibility and rationality of the blade fatigue life assessment test from the perspective of theory and experiment is demonstrated as well.A reference for the fatigue life assessment of liquid rocket engine turbine blades and other components was provides in this paper.
作者
刘士杰
刘恒
刘继超
梁国柱
张军伟
王慧
LIU Shi-jie;LIU Heng;LIU Ji-chao;LIANG Guo-zhu;ZHANG Jun-wei;WANG Hui(Beijing Aerospace Propulsion Institute Laboratory of Science and Technology on Cryogenic Liquid Propulsion of CASC,100076,China;Beijing Machine Tool Research Institute Co.,Ltd.,Beijing 100102,China;School of Astronautics,Beijing University of Aeronautics and Astronautics,Beijing,102206,China;Beijing Institute of Space Launch Technology,Beijing 100076,China)
出处
《强度与环境》
CSCD
2021年第2期38-44,共7页
Structure & Environment Engineering
